Airplane windscreen frame assembly

Abstract

The present application relates to a kind of aircraft windscreen frame skeleton assemblies, comprising: window frame skeleton, window frame skeleton includes around the main windscreen of aircraft main windscreen mouth frame and around the side windscreen of aircraft side windscreen mouth frame, and main windscreen mouth frame and side windscreen mouth frame are integrally formed with corresponding main windscreen and side windscreen by the form of tight fit installation cooperation, realize the load transfer of aircraft.Two main windscreen mouth frame directly contact and are connected, and main windscreen mouth frame and side windscreen mouth frame are also directly contacted and are connected.The butt joint design of the mouth frame of four integral window frame skeletons and the use of connecting band plate at mouth frame butt joint section make the force transmission route of window frame at connection section more directly, realize higher transmission efficiency, higher structural efficiency, under the premise of meeting the bearing design demand, since window frame section form is simple, manufacturing difficulty and manufacturing cost are greatly reduced.

Description

Technical Field

[0001] This invention relates to an aircraft windshield frame skeleton assembly, specifically, to a load-bearing windshield frame skeleton and the structure for direct connections between the frame skeletons. This invention relates to the design of an integral load-bearing aircraft windshield frame, belonging to the field of design and connection methods for aircraft windshield frame skeletons. Background Technology

[0002] The aircraft windshield frame assembly (also known as the windshield sunroof frame assembly) is located in the cockpit canopy area at the nose of the aircraft, directly in front of the pilot. It is the most important structural component in the entire canopy area and the first part to be positioned during the assembly of the upper part of the nose. The connection method, shape control, and manufacturability of the frame assembly must be considered holistically.

[0003] In existing technologies, the main types of aircraft windshields and their window frame frames are as follows:

[0004] 1. The A320 series aircraft has a flat plate windshield with a corresponding flat window frame. The ventilation window and the rear side window are separated by a closed frame. The frames of the windshield and side windows are connected to the other frames and panels by joints.

[0005] 2. The B737-700 aircraft features a flat, threaded windshield with a corresponding flat window frame frame. Adjacent window frames are sequentially joined together, and the entire structure is manufactured using die forging. The front and lower parts of this die forging have flanges that connect to the fuselage frame and fuselage stringer. The flanges extend from the die forging and connect to the corresponding fuselage stringer and fuselage frame via joints.

[0006] 3. The ERJ-190 aircraft has a curved main windshield with a segmented frame, requiring a central support column and connectors to connect it to the fuselage frame and fuselage stringers.

[0007] However, in existing technologies, the windshields used in in-service aircraft generally do not participate in the overall force transmission of the fuselage. To ensure that the nose canopy area meets the requirements for bird strike resistance and differential pressure loads during normal flight, the window frame itself requires high strength and rigidity. The window frame requires a central pillar and its overall structure is relatively thick and heavy.

[0008] In addition, due to structural strength requirements, the window frame frames selected for in-service models are all segmented assembly forms that are connected to each other, rather than integral window frames. They have many structural components, complex and diverse connection forms, high manufacturing difficulty, and difficulty in ensuring assembly accuracy.

[0009] Currently, more advanced aircraft, such as the C919, are beginning to adopt large-area double-curvature load-bearing windshields. The windshields can withstand and transmit a certain load at the nose of the aircraft, so the load-bearing capacity requirements of the window frame are correspondingly reduced.

[0010] Therefore, there is a need for lighter and easier-to-manufacture window frame skeletons for load-bearing windshield designs. Summary of the Invention

[0011] To address the aforementioned problems in the prior art, the present invention aims to provide an aircraft windshield frame skeleton assembly to meet the frame skeleton requirements corresponding to load-bearing windshield designs, thereby reducing the manufacturing difficulty and cost of the frame while meeting load-bearing requirements, and increasing its processing and assembly positioning accuracy.

[0012] To address the aforementioned problems, this invention provides an aircraft windshield frame skeleton assembly based on a load-bearing windshield. In a first example of this aircraft windshield frame skeleton assembly, the assembly includes a frame skeleton comprising a main windshield frame surrounding the main windshield and side windshield frames surrounding the side windshields. The main windshield frames and side windshield frames are installed and fitted together with the corresponding main windshields and side windshields through a tight fit, wherein the two main windshield frames are in direct contact and are mated together, and the main windshield frames and side windshield frames are in direct contact and are mated together.

[0013] In a second example of the aircraft windshield frame skeleton assembly, the first example may be optionally included, wherein the main windshield frame is a single piece of integral frame and the side windshield frames are single pieces of integral frames.

[0014] In a third example of the aircraft windshield frame skeleton assembly, one or more of the first and second examples may be included, with the two main windshield frames in direct contact and joined together to form an "I" shape.

[0015] In the fourth example of the aircraft windshield frame skeleton assembly, one or more of the first to third examples may be included. The main windshield frame is Z-shaped, and the side windshield frames are I-shaped. The corresponding main windshield frames and corresponding side windshield frames are in direct contact and mating connection. Furthermore, the mating main windshield frames and side windshield frames are further reinforced with flanges on the basis of the Z-shape to form a "U" shape. The shape of the character "".

[0016] In the fifth example of the aircraft windshield frame skeleton assembly, one or more of the first to fourth examples may be included. At the location where the two main windshield frames directly contact and are joined together, and at the location where the corresponding main windshield frame and the side windshield frame directly contact and are joined together, the aircraft windshield frame skeleton assembly also includes a window frame connecting strip plate. The window frame connecting strip plate is installed at the mating interface of the corresponding left and right main windshield frames, or at the mating interface of the corresponding main windshield frame and the side windshield frame. The load-bearing windshield is connected to the corresponding window frame skeleton by fasteners, and the fasteners pass through the window frame connecting strip plate, connecting the load-bearing windshield, the window frame connecting strip plate and the window frame skeleton into a whole.

[0017] In the sixth example of the aircraft windshield frame skeleton assembly, one or more of the first to fifth examples may be included, wherein the main windshield frame and the side windshield frame in the frame skeleton are connected to the fuselage frame and the fuselage stringer by a flange extending from the frame skeleton.

[0018] In the seventh example of the aircraft windshield frame skeleton assembly, one or more of the first to sixth examples may be included, and the flange extending from the frame skeleton is connected to the fuselage frame and fuselage stringer by a reinforcing member.

[0019] The design of the integral aircraft windshield frame skeleton assembly of this invention adopts a direct mating connection design at the original central and side column positions, reducing the overall thickness of the window frame. The original columns extend upwards and downwards, directly docking or overlapping with the surrounding structure, eliminating the need for connecting joints. The mating connection design of the four integral window frame skeletons and the use of connecting plates at the joint sections directly alter the force transmission path at the connection sections, achieving higher load transfer efficiency and higher structural utilization efficiency. While meeting load-bearing design requirements, the simple window frame cross-section significantly reduces manufacturing difficulty and cost. Attached Figure Description

[0020] To describe embodiments in which the above and other features of the invention are obtained, a more detailed description of the invention, briefly described above, will be presented with reference to exemplary embodiments of the invention shown in the accompanying drawings. It is to be understood that these drawings depict only exemplary embodiments of the invention and should not be considered as limiting its scope; the invention will be described and explained using the drawings and with the aid of additional features and details. In the drawings:

[0021] Figure 1 This is a frontal perspective view of the position where the two integral main windshield frames of the aircraft windshield frame skeleton assembly are joined together according to a preferred embodiment of the present invention.

[0022] Figure 2This is a frontal perspective view of the position where the main windshield frame and the side windshield frame of the aircraft windshield frame skeleton assembly are joined together according to a preferred embodiment of the present invention.

[0023] Figure 3 This is a three-dimensional schematic diagram of the connection between the window frame skeleton and the fuselage stringer and fuselage frame according to a preferred embodiment of the present invention.

[0024] Figures 1 to 3 The figures are drawn roughly to scale; however, the dimensions in the accompanying drawings are merely illustrative and not necessarily to scale, but are intended to make the illustration clearer. Other relative dimensions may be used in other embodiments.

[0025] Throughout this and all subsequent content, the same features appearing in different figures are indicated by the same or similar reference numerals.

[0026] List of reference numerals in the attached diagram:

[0027] 10 Load-bearing windshield

[0028] 11 Main windshield

[0029] 12 Side windshields

[0030] 20 Window frame skeleton

[0031] 21 Main windshield frame

[0032] 22 Side windshield frame

[0033] 23 Window frame connecting strip plate Detailed Implementation

[0034] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0035] Figure 1 The diagram schematically illustrates a front cross-sectional perspective view of the connection point between the two main windshield frames of an aircraft windshield frame skeleton assembly according to a preferred embodiment of the present invention. The aircraft windshield frame skeleton assembly according to the present invention mainly includes a window frame skeleton 20.

[0036] The window frame skeleton 20 may include two main windshield frames 21 corresponding to the main windshield 11 and two side windshield frames 22 corresponding to the side windshields 12.

[0037] In a preferred embodiment, both the main windshield frame 21 and the side windshield frame 22 are integral frames, reducing manufacturing costs. Due to the use of a load-bearing windshield, the load-bearing requirements of the window frame skeleton of this invention are correspondingly reduced. The window frame skeleton 20 adopts a design of four integral window frames combined with each other, so that the curved surface of the window frame skeleton 20 and the load-bearing windshield 10 are integrated, achieving a high degree of fit with the windshield's overall pressure plate, meeting the requirement of a smooth appearance, and effectively preventing air leakage.

[0038] exist Figure 1 In the middle, the two main windshield frames 21 are directly joined together to form an "I" shape. Preferably, since a load-bearing windshield is used, the load-bearing requirements of the window frame skeleton of the present invention are correspondingly reduced. Therefore, this "I" beam can serve as the central column of the load-bearing windshield, eliminating the need to install a heavy single central column.

[0039] Now go to Figure 2 , Figure 2 The diagram schematically shows a frontal perspective view of the position where the main windshield frame and the side windshield frame of the aircraft windshield frame skeleton assembly of a preferred embodiment of the present invention are joined together.

[0040] exist Figure 2 In the middle, the main windshield frame 21 is Z-shaped, and the side windshield frame 22 is I-shaped.

[0041] The left or right main windshield frame 21 directly contacts and aligns with the corresponding side windshield frame 22, and a flange is added to the "Z" shape to further form a "Z" shape. The aforementioned "I"-shaped beam can serve as the side support column for a load-bearing windshield, and... The I-beam can improve the overall bending resistance and at the same time provide enough open space for the cutting tools used in manufacturing, which greatly reduces the manufacturing difficulty.

[0042] from Figure 1 and Figure 2 As can be seen, at the locations where the two main windshield frames 21 directly meet and connect, and at the locations where the corresponding main windshield frame 21 and side windshield frame 22 directly meet and connect, there is also a window frame connecting strip 23. The window frame connecting strip 23 can be fixed to the corresponding main windshield frame 21, or it can be fixed to both the corresponding main windshield frame 21 and the side windshield frame 22.

[0043] The load-bearing windshield 10 is installed to the window frame skeleton 20 using known connectors. In a preferred embodiment, one end of these connectors is connected to the load-bearing windshield 10, and the other end can be connected to the window frame connecting strip 23 and the window frame skeleton 20. Adding the window frame connecting strip 23 to the outside of the window frame skeleton 20 aims to make the load transfer path at the aforementioned central and side column positions more direct, thereby improving the overall structural load transfer efficiency.

[0044] Now go to Figure 3 , Figure 3 A perspective view illustrating the connection between the window frame skeleton and the fuselage stringer and fuselage frame according to a preferred embodiment of the present invention is shown.

[0045] The main windshield frame 21 and side windshield frames 22 of the window frame skeleton 20 are connected to the fuselage frame and fuselage stringer via flanges extending from the window frame skeleton 20. Preferably, since a load-bearing windshield is used, the load-bearing requirements of the window frame skeleton of the present invention are correspondingly reduced. Therefore, the flanges extending from the window frame skeleton 20 can be connected to the fuselage frame and fuselage stringer using reinforcing members, while still meeting the load-bearing requirements at the nose of the aircraft, without the need for joint connections. Therefore, the number of parts required for connection is reduced, and processing and assembly are convenient.

[0046] The aircraft windshield frame skeleton assembly according to the present invention reduces the overall thickness of the window frame by using a design in which the openings of the window frame skeleton are directly connected to each other at the original central pillar and side pillar positions.

[0047] The window frame extends vertically and horizontally from the existing columns, directly connecting or overlapping with the surrounding structure, eliminating the need for connecting joints. The structural cross-section formed at the column interface of the integrated window frame incorporates an external connecting plate, making the load transfer path more direct and improving the overall structural load transfer efficiency.

[0048] The window frame mating design and the use of connecting strips allow for a direct change in the force transmission path at the connection sections of each frame of the window frame skeleton, resulting in higher structural efficiency, a wider driving field of vision, better aerodynamic shape and better manufacturability. At the same time, it reduces manufacturing costs while meeting load-bearing requirements, and still meets the load-bearing capacity required during assembly.

[0049] In order to make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention have been clearly and completely described above in conjunction with the specific embodiments and accompanying drawings.

[0050] Although various embodiments have been described above, it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of them, and are presented by way of example rather than limitation. It will be apparent to those skilled in the art that the disclosed subject matter may be implemented in other specific forms without departing from its spirit and essential characteristics.

[0051] Therefore, the embodiments described above are to be considered exemplary and not restrictive in all respects, and are not intended to limit the invention in any way.

[0052] Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this invention. This disclosure also includes various modifications and equivalent variations. In addition, various combinations and methods, further including only one element, one or more or less other combinations and methods, also fall within the scope and concept of this disclosure.

Claims

1. An aircraft windshield frame skeleton assembly, characterized in that, The aircraft windshield frame skeleton assembly includes: The window frame frame (20) includes a main windshield frame (21) surrounding the main windshield (11) of the aircraft and a side windshield frame (22) surrounding the side windshields (12) of the aircraft. The main windshield frame (21) and the side windshield frame (22) are installed and fitted together with the corresponding main windshield (11) and the side windshield (12) in a tight fit to form an integral unit. Two of the main windshield frames (21) are in direct contact and are joined together, and The main windshield frame (21) and the side windshield frame (22) are in direct contact and are connected. Where the two main windshield frames (21) are in direct contact and connected, and where the corresponding main windshield frame (21) and the side windshield frame (22) are in direct contact and connected, the aircraft windshield frame skeleton assembly also includes a window frame connecting strip plate (23). The window frame connecting strip plate (23) is installed at the mating interface of the corresponding left and right main windshield frames (21), or at the mating interface of the corresponding main windshield frame (21) and the side windshield frame (22). The load-bearing windshield (10) is connected to the corresponding window frame frame (20) by fasteners, and the fasteners pass through the window frame connecting strip (23), connecting the load-bearing windshield (10), the window frame connecting strip (23) and the window frame frame (20) into a whole. The window frame connecting strip (23) is sandwiched between the load-bearing windshield (10) and the window frame skeleton (20).

2. The aircraft windshield frame skeleton assembly according to claim 1, characterized in that, The main windshield frame (21) is a single, integral frame, and The side windshield frame (22) is a single, integral frame.

3. The aircraft windshield frame skeleton assembly according to claim 1, characterized in that, The two main windshield frames (21) are in direct contact and are joined together to form an "I" shape.

4. The aircraft windshield frame skeleton assembly according to claim 1, characterized in that, The main windshield frame (21) is Z-shaped, and the side windshield frame (22) is Γ-shaped. The corresponding main windshield frame (21) and the corresponding side windshield frame (22) are in direct contact and are connected. The main windshield frame (21) and the side windshield frame (22) connected by a joint are further reinforced with flanges on the basis of a "Z" shape to form a "Z" shape. The shape of the character "".

5. The aircraft windshield frame skeleton assembly according to claim 1, characterized in that, The main windshield frame (21) and the side windshield frame (22) in the window frame skeleton (20) are connected to the fuselage frame and fuselage stringer by a flange extending from the window frame skeleton (20).

6. The aircraft windshield frame skeleton assembly according to claim 5, characterized in that, The flange extending from the window frame skeleton (20) is connected to the fuselage frame and the fuselage stringer by a reinforcing member.

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